def polaire_equi(P):
q = 0
mss = [0.2, 1]
alphas = np.arange(ut.rad_of_deg(-10), ut.rad_of_deg(20), ut.rad_of_deg(1))
km = 0.1
for ms in mss:
P.set_mass_and_static_margin(km, ms)
dphrs = []
dphrs = np.array([(P.ms * P.CLa * (alpha - P.a0) - P.Cm0) / P.Cmd
for alpha in alphas])
CLe = []
CLe = [
dyn.get_aero_coefs(dyn.va_of_mach(0.7, 7000), alpha, q, dphr, P)[0]
for alpha, dphr in zip(alphas, dphrs)
]
Cxe = [
dyn.get_aero_coefs(dyn.va_of_mach(0.7, 7000), alpha, q, dphr, P)[1]
for alpha, dphr in zip(alphas, dphrs)
]
finesse = [CL / Cx for Cx, CL in zip(Cxe, CLe)]
fmax = np.max(finesse)
idmax = np.argmax(finesse)
print(fmax)
plt.plot([0, Cxe[idmax]], [0, CLe[idmax]])
plt.plot(Cxe, CLe)
label1 = patches.Patch(color='blue', label='fmax (ms = 0.2)')
label2 = patches.Patch(color='green', label='Polaire (ms = 0.2)')
label3 = patches.Patch(color='red', label='fmax (ms = 1)')
label4 = patches.Patch(color='cyan', label='Polaire (ms = 1)')
plt.legend(loc='upper left', handles=[label1, label2, label3, label4])
ut.decorate(plt.gca(), "Evolution de la polaire équilibrée",
'Coefficient de trainée équilibrée',
'Coefficient de portance équilibrée')
plt.show
def get_CL_alpha(
va, q, dphr, P, alpha, nb
): # calcule CL en fonction de l'angle d'incidence alpha , (vitesse m/s,vitesse de tangage rad/sec, angle de braquage de l'empennage horozontal en rad, intervalle d'incidnce alpha rad, nombre de points)
angle_alpha = np.linspace(alpha[0], alpha[1], nb)
CL = np.array([
dynamic.get_aero_coefs(va, alpha, q, dphr, P)[0]
for alpha in angle_alpha
])
return utils.deg_of_rad(angle_alpha), CL #angle_alpha en degré
def CLE_alpha(va, q, P, alpha, nb, ms):
angle_alpha = np.linspace(interv_alpha[0], interv_alpha[1], nb)
dphr = np.array([
-(P.Cm0 - ms * P.CLa * (k - P.a0) + P.Cmq * P.lt / va * q) / P.Cmd
for k in angle_alpha
])
CLE = np.array([
dynamic.get_aero_coefs(va, alpha, q, dphr[i], P)[0]
for i, alpha in enumerate(angle_alpha)
])
return utils.deg_of_rad(angle_alpha), CLE
def CLE_alpha(
va, q, P, alpha, nb, ms
): #coefficident de portance equilibrée Cle lorsque dphr=dphre, (idem)
angle_alpha = np.linspace(alpha[0], alpha[1], nb)
dphr = np.array([
-(P.Cm0 - ms * P.CLa * (k - P.a0) + P.Cmq * P.lt / va * q) / P.Cmd
for k in angle_alpha
])
CLE = np.array([
dynamic.get_aero_coefs(va, alpha, q, dphr[i], P)[0]
for i, alpha in enumerate(angle_alpha)
])
return utils.deg_of_rad(angle_alpha), CLE
def evol_coeff_portance(P):
alphas = np.arange(ut.rad_of_deg(-10), ut.rad_of_deg(20), ut.rad_of_deg(1))
dphrs = [ut.rad_of_deg(-30), ut.rad_of_deg(20)]
q = 0
Cz_tab1 = []
Cz_tab2 = []
for alpha in alphas:
coeff_portance1 = dyn.get_aero_coefs(dyn.va_of_mach(0.7, 7000), alpha,
q, dphrs[0], P)
Cz_tab1.append(coeff_portance1[0])
coeff_portance2 = dyn.get_aero_coefs(dyn.va_of_mach(0.7, 7000), alpha,
q, dphrs[1], P)
Cz_tab2.append(coeff_portance2[0])
plt.plot(ut.deg_of_rad(alphas), Cz_tab1, 'r')
plt.plot(ut.deg_of_rad(alphas), Cz_tab2, 'b')
label1 = patches.Patch(color='red', label='dPHR1 = -30°')
label2 = patches.Patch(color='blue', label='dPHR2 = 20°')
plt.legend(loc='upper left', handles=[label1, label2])
ut.decorate(plt.gca(),
title="Evolution du Cz en fonction de l'incidence",
xlab='Incidence',
ylab='Cz')
plt.show()
def coeff_CLe(a, m_s):
alpha = np.linspace(a[0], a[1], 100)
alpha0 = PLANE.a0 * 180 / pi
plt.figure(5)
for m in m_s:
PLANE.set_mass_and_static_margin(km, m)
dphre = (PLANE.Cm0 - PLANE.ms * PLANE.CLa * ((alpha - alpha0)*pi/180)) / (Vt * PLANE.CLat)
CL = dynamic.get_aero_coefs(va, alpha*pi/180, 0, dphre, PLANE)[0]
plt.plot(alpha, CL, label='$m_s={}$'.format(m))
plt.xlabel("$\\alpha_{eq}$")
plt.ylabel("$C_{L_e}$")
plt.title('$\\alpha_e\\mapsto C_L$')
plt.legend()
plt.savefig(file + "q5" + format)
plt.show()
def coeff_Cm(a, m_s):
dphr = 0
alpha = np.linspace(a[0], a[1], 100)
m_s_original = PLANE.ms
plt.figure(2)
for m in m_s:
PLANE.set_mass_and_static_margin(km, m)
Cm = dynamic.get_aero_coefs(va, alpha*pi/180, 0, dphr, PLANE)[2]
plt.plot(alpha, Cm, label="$m_s={}$".format(m))
plt.xlabel("$\\alpha$")
plt.ylabel("$C_m$")
plt.title("$\\alpha \\mapsto C_m$")
plt.legend()
plt.savefig(file + "q3" + format)
plt.show()
PLANE.set_mass_and_static_margin(km, m_s_original)
def polaire(a, m_s):
alpha = np.linspace(a[0], a[1], 100)
plt.figure(6)
fmax = np.zeros(len(m_s))
for i, m in enumerate(m_s):
PLANE.set_mass_and_static_margin(km, m)
dphre = (PLANE.Cm0 - PLANE.ms * PLANE.CLa * (alpha*pi/180)) / (Vt * PLANE.CLat)
CL, CD = dynamic.get_aero_coefs(va, alpha*pi/180, 0,dphre, PLANE)[0:2]
plt.plot(CD, CL, label='$m_s={}$'.format(m))
fmax[i] = max(CL / CD)
plt.title('Polaire équilibrée')
plt.xlabel('$C_D$')
plt.ylabel('$C_L$')
plt.legend()
plt.savefig(file + "polaire" + format)
plt.show()
return fmax
def coeff_Cl(a, delta_PHR):
"""
:param a: a list of two angles (min an max) in degree !
:param delta_PHR: degree !
:return:
"""
alpha = np.linspace(a[0], a[1], 100)
plt.figure(1)
for d in delta_PHR:
Cl = dynamic.get_aero_coefs(va, alpha*pi/180, 0, d*pi/180, PLANE)[0]
plt.plot(alpha, Cl, label="$\delta_{{PHR}}={:.0f}$".format(d))
plt.xlabel("$\\alpha$")
plt.ylabel("$C_L$")
plt.title("$\\alpha\\mapsto C_l$")
plt.legend()
plt.savefig(file + "q2" + format)
plt.show()
def evol_CLe(P):
q = 0
mss = [0.2, 1]
alphas = np.arange(ut.rad_of_deg(-10), ut.rad_of_deg(20), ut.rad_of_deg(1))
km = 0.1
for ms in mss:
P.set_mass_and_static_margin(km, ms)
dphrs = []
dphrs = np.array([(P.ms * P.CLa * (alpha - P.a0) - P.Cm0) / P.Cmd
for alpha in alphas])
CLe = []
CLe = [
dyn.get_aero_coefs(dyn.va_of_mach(0.7, 7000), alpha, q, dphr, P)[0]
for alpha, dphr in zip(alphas, dphrs)
]
plt.plot(ut.deg_of_rad(alphas), CLe)
label1 = patches.Patch(color='blue', label='ms = 0.2')
label2 = patches.Patch(color='green', label='ms = 1')
plt.legend(loc='upper left', handles=[label1, label2])
ut.decorate(plt.gca(), "Evolution de CLe en fonction de l'incidence",
'Incidence', 'Coefficient de portance équilibrée')
plt.show